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1.7 to 2.9 km/s (3800 to 6500 mi/h) for liquid monopropellants; 2.9 to 4.5 km/s (6500 to 10100 mi/h) for liquid bipropellants; 2.1 to 3.2 km/s (4700 to 7200 mi/h) for solid propellants; As a note of interest, v e is sometimes referred to as the ideal exhaust gas velocity because it based on the assumption that the exhaust gas behaves as an ...
A de Laval nozzle (or convergent-divergent nozzle, CD nozzle or con-di nozzle) is a tube which is pinched in the middle, with a rapid convergence and gradual divergence. It is used to accelerate a compressible fluid to supersonic speeds in the axial (thrust) direction, by converting the thermal energy of the flow into kinetic energy .
1 ideal exhaust velocity. 22 comments. 2 Merged with other articles. 3 comments. 3 Quite a long sentence. 2 comments. 4 ...
The Jumo 004 had a large area for starting to prevent overheating the turbine and a smaller area for take-off and flight to give higher exhaust velocity and thrust. The 004's Zwiebel possessed a 40 cm (16 in) range of forward/reverse travel to vary the exhaust nozzle area, driven by an electric motor-driven mechanism within the body's divergent ...
Characteristic velocity or , or C-star is a measure of the combustion performance of a rocket engine independent of nozzle performance, and is used to compare different propellants and propulsion systems. c* should not be confused with c, which is the effective exhaust velocity related to the specific impulse by: =. Specific impulse and ...
A rocket's required mass ratio as a function of effective exhaust velocity ratio. The classical rocket equation, or ideal rocket equation is a mathematical equation that describes the motion of vehicles that follow the basic principle of a rocket: a device that can apply acceleration to itself using thrust by expelling part of its mass with high velocity and can thereby move due to the ...
Water, while under pressure, is heated up to a high temperature (approx. 250–500 °C). As the hot water goes through the nozzle (usually a de Laval nozzle) and the pressure reduces, the water flashes to steam pressing on the nozzle, and leaving at high speed. By the recoil the rocket accelerates in the opposite direction to the steam.
For a supersonic flow in an expanding conduit (M > 1 and dA > 0), the flow is accelerating (dV > 0). For a supersonic flow in a converging conduit (M > 1 and dA < 0), the flow is decelerating (dV < 0). At a throat where dA = 0, either M = 1 or dV = 0 (the flow could be accelerating through M = 1, or it may reach a velocity such that dV = 0).
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